Gas turbine combustion burner
View Patent ↗In a gas-turbine combustion burner which is provided, at a distal end thereof, with a fuel spraying hole that sprays fuel into a combustion region formed inside a combustion cylinder of a gas-turbine combustor and in which a fuel flow path that guides the fuel, which is supplied from a fuel source, to the fuel spraying hole is formed in the interior thereof, the impedance of a fuel supply system that guides the fuel from the fuel source to the fuel spraying hole is set so that propagation of pressure fluctuations from the combustion region to the fuel supply system becomes an allowable level or less.
1. A gas-turbine combustion burner which is provided, at a distal end thereof, with a fuel injector that sprays fuel through an outlet thereof into a combustion region formed inside a combustion cylinder of a gas-turbine combustor; wherein a fuel flow path that guides the fuel, which is supplied from a fuel source, to the fuel injector is formed in the interior of the burner,
wherein the fuel injector comprises a tube-shaped portion which protects from an outer circumferential edge of the distal end of the burner,
wherein the tube-shaped portion comprises an internal fuel passage extending from an inlet to the outlet of the fuel injector, the internal fuel passage in fluid communication with the fuel flow path,
wherein a baffle plate having a constant-diameter opening is provided at an intermediate position in the fuel flow path,
wherein a value of an acoustic resistance for a flow velocity of fuel flowing through the fuel flow path is determined from a normal-incidence sound absorption coefficient, which indicates the ratio of a pressure wave absorbed between the baffle plate and the outlet with respect to the pressure wave propagated from the combustion region upstream of the baffle plate, and
wherein the diameter of the opening is set so that the acoustic resistance for the flow velocity of fuel flowing through the fuel flow path is larger than an acoustic resistance at which the normal-incidence sound absorption coefficient is at a desired value.
2. A gas-turbine combustion burner according to claim 1 , wherein the baffle plate is made of a sound-absorbing material.
3. A gas-turbine combustion burner which is provided, at a distal end thereof, with a fuel injector that sprays fuel from an outlet thereof into a combustion region formed inside a combustion cylinder of a gas-turbine combustor; wherein a fuel flow path that guides the fuel, which is supplied from a fuel source, to the fuel injector is formed in the interior of the burner,
wherein the fuel injector comprises a tube-shaped portion which projects from an outer circumferential edge of the distal end of the burner,
wherein the tube-shaped portion comprises an internal fuel passage having an inlet and a fuel passage length extending from the inlet to the outlet of the fuel injector, the internal fuel passage in fluid communication with the fuel flow path,
wherein the internal fuel passage further comprises a reduced-diameter portion that gradually reduces in diameter from the inlet to at least one constant diameter portion located downstream from the reduced-diameter portion, and a wide-diameter portion having an inner diameter which is larger than an inner diameter of the at least one constant diameter portion, located downstream from the at least one constant-diameter portion,
wherein a value of an acoustic resistance for a flow velocity of fuel flowing through the internal fuel passage is determined from a normal-incidence sound absorption coefficient, which indicates the ratio of a pressure wave absorbed in the fuel injector with respect to the pressure wave propagated from the combustion region through and upstream of the fuel injector, and
wherein a diameter of the internal fuel passage is set so that the acoustic resistance for the flow velocity of fuel flowing through the internal fuel passage is larger than an acoustic resistance at which the normal-incidence sound absorption coefficient is at a desired value.
4. A gas-turbine combustion burner according to claim 3 , wherein the reduced-diameter portion extends to a point at ¼ of the fuel passage length, a first constant-diameter portion that extends from the point at ¼ of the fuel passage length to a point at 2/4 of the fuel passage length, the wide-diameter portion extends from the point at 2/4 of the fuel passage length to a point at ¾ of the fuel passage length, and a second constant-diameter portion that extends from the point at ¾ of the fuel passage length to the outlet of the fuel injector.
5. A gas-turbine combustion burner according to claim 4 , wherein the inner diameter of the wide-diameter portion of the internal fuel passage is set to be 1.5 times the inner diameter of the first constant-diameter portion of the internal fuel passage.
6. A gas-turbine combustion burner according to claim 3 , wherein the reduced-diameter portion extends to a point at ⅓ of the fuel passage length, the constant-diameter portion extends from the point at ⅓ of the fuel passage length to a point at ⅔ of the fuel passage length, and the wide-diameter portion extends from the point at ⅔ of the fuel passage length to the outlet of the fuel injector.
7. A gas-turbine combustion burner according to claim 6 , wherein the inner diameter of the wide-diameter portion of the internal fuel passage is set to be 1.5 to 5 times the inner diameter of the constant-diameter portion of the internal fuel passage.
8. A gas-turbine combustor comprising a gas-turbine combustion burner according to claim 3 .